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Nonlinear Dynamics of a Helicopter Model in Ground ResonanceAn approximate theoretical method is presented which determined the limit cycle behavior of a helicopter model which has one or two nonlinear dampers. The relationship during unstable ground resonance oscillations between lagging motion of the blades and fuselage motion is discussed. An experiment was carried out on using a helicopter scale model. The experimental results agree with those of the theoretical analysis.
Document ID
19860005814
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Tang, D. M. (Duke Univ. Durham, NC, United States)
Dowell, E. H. (Duke Univ. Durham, NC, United States)
Date Acquired
August 12, 2013
Publication Date
November 1, 1985
Publication Information
Publication: NASA. Ames Research Center Rotorcraft Dynamics 1984
Subject Category
Aircraft Stability And Control
Accession Number
86N15284
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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